Components for gas turbine engines

ABSTRACT

Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional PatentApplication Ser. No. 63/304,242 filed Jan. 28, 2022, the disclosure ofwhich is incorporated herein by reference in its entirety.

BACKGROUND

Illustrative embodiments pertain to the art of turbomachinery, andspecifically to turbine rotor components.

Gas turbine engines are rotary-type combustion turbine engines builtaround a power core made up of a compressor, combustor and turbine,arranged in flow series with an upstream inlet and downstream exhaust.The compressor compresses air from the inlet, which is mixed with fuelin the combustor and ignited to generate hot combustion gas. The turbineextracts energy from the expanding combustion gas, and drives thecompressor via a common shaft. Energy is delivered in the form ofrotational energy in the shaft, reactive thrust from the exhaust, orboth.

The compressor and turbine sections are typically subdivided into anumber of stages, which are formed of alternating rows of rotor bladeand stator vane airfoils. The airfoils are shaped to turn, accelerateand compress the working fluid flow, or to generate lift for conversionto rotational energy in the turbine.

Airfoils may incorporate various cooling cavities located adjacentexternal side walls. Such cooling cavities are subject to both hotmaterial walls (exterior or external) and cold material walls (interioror internal). Although such cavities are designed for cooling portionsof airfoil bodies, various cooling flow characteristics can cause hotsections where cooling may not be sufficient. Accordingly, improvedmeans for providing cooling within an airfoil may be desirable.

BRIEF DESCRIPTION

According to some embodiments, airfoil assemblies for gas turbineengines are provided. The airfoil assemblies include an airfoil bodyhaving a leading edge, a trailing edge, a pressure side wall, and asuction side wall, the airfoil body extending in a radial directionbetween an outer diameter end and an inner diameter end, wherein theairfoil defines a leading edge cavity bounded by interior surfaces ofthe airfoil body along the leading edge, the pressure side wall, thesuction side wall, and an interior rib extending between the pressureside wall and the suction side wall. A leading edge baffle is installedwithin the leading edge cavity. A first forward radially extending railextends into the leading edge cavity and extends between the innerdiameter end and the outer diameter end in a radial direction, the firstforward radially extending rail positioned on the pressure side wall ofthe airfoil body. A second forward radially extending rail extends intothe leading edge cavity and extends between the inner diameter end andthe outer diameter end in the radial direction, the second forwardradially extending rail positioned on the suction side wall of theairfoil body.

A first aft radially extending rail extends into the leading edge cavityand extends between the inner diameter end and the outer diameter end inthe radial direction, the first aft radially extending rail positionedon the pressure side wall of the airfoil body. A second aft radiallyextending rail extends into the leading edge cavity and extends betweenthe inner diameter end and the outer diameter end in the radialdirection, the second aft radially extending rail positioned on thesuction side wall of the airfoil body. Each of the first and secondforward radially extending rails are segmented in the radial direction,a showerhead radial channel is defined between an interior surface ofthe airfoil body along the leading edge, an exterior surface of theleading edge baffle, and each of the first and second forward radiallyextending rails, a pressure side radial flow channel is defined betweenan interior surface of the airfoil body along the pressure side wall, anexterior surface of the leading edge baffle, the first forward radiallyextending rail, and the first aft radially extending rail, a suctionside radial flow channel is defined between an interior surface of theairfoil body along the suction side wall, an exterior surface of theleading edge baffle, the second forward radially extending rail, and thesecond aft radially extending rail, and an aft channel is definedbetween an interior surface of the airfoil body along the suction sidewall, the pressure side wall, and the interior rib, an exterior surfaceof the leading edge baffle, and the first and second aft radiallyextending rails.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may include aplurality of showerhead apertures formed on the leading edge, pressureside, or suction side of the airfoil body and fluidly connected to theshowerhead, pressure side, or suction side radial flow channels.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includeone or more heat transfer augmentations features arranged on an interiorsurface of the airfoil body along at least one of the showerhead radialchannel, the pressure side radial flow channel, the suction side radialflow channel, or the aft channel.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises an aft wall having at least onetrailing edge impingement aperture arranged to direct an impingementflow against the interior rib of the airfoil body.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includean inner diameter forward collar formed about a portion of the innerdiameter end of the leading edge cavity.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the inner diameter forward collar defines a blockage of at leastone of the showerhead radial channel, the pressure side radial flowchannel, and the suction side radial flow channel to prevent radialthrough-flow at the inner diameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may include acontinuous or discontinuous outer diameter forward collar that isconfigured to augment the cooling airflow resupply apertures at theouter diameter end of the airfoil body from at least one of the pressureside radial flow channel, the suction side radial flow channel, or theleading edge flow channel into the showerhead radial channel.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may include acontinuous or discontinuous outer diameter forward collar which may befabricated as a feature of the airfoil casting, or as acircumferentially extending shelf or flange of the baffle component,which may include at least one supply feed aperture.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the inner diameter forward collar is configured to direct air flowat the inner diameter end of the airfoil body from at least one of thepressure side radial flow channel or the suction side radial flowchannel into the showerhead radial channel.

In addition to one of more of the features described above, furtherembodiments of the airfoil assemblies may include at least one collarthat may be positioned at one or more radial locations to partition,segregate, and tailor a radial and spanwise distribution of cooling flowto achieve optimal convective and film cooling thermal performance.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle is capped at an inner diameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the aft channel is a throughflow channel configured to supplycooling flow into at least an inner diameter platform.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises a leading edge feed aperture atan outer diameter end thereof, the leading edge feed aperture configuredto direct a cooling flow into the showerhead radial channel at an outerdiameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises at least one side feed aperturearray at an outer diameter end thereof, the at least one side feedaperture array configured to direct a cooling flow into at least one ofthe pressure side radial flow channel or the suction side radial flowchannel at an outer diameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includeat least one resupply aperture on the leading edge baffle arranged at aposition between the at least one side feed aperture array and the innerdiameter end of the leading edge baffle.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises at least one aft feed aperturearray at an outer diameter end thereof, the at least one aft feedaperture array configured to direct a cooling flow into the aft channelat an outer diameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises a solid portion between at leastone feed aperture proximate an outer diameter end of the leading edgebaffle and an inner diameter end of the leading edge baffle.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises at least one standoff shelf orstandoff protrusion feature configured to engage with at least one ofthe first forward radially extending rail, the second forward radiallyextending rail, the first aft radially extending rail, or the second aftradially extending rail.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat a standoff gap is formed between the at least one standoff shelf orstandoff protrusion feature and the respective rail to which the atleast one standoff shelf or standoff protrusion feature engages.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the standoff gap defines a throughflow channel for cooling air.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat each of the first and second aft radially extending standoff railsare substantially continuous in the radial direction and provide fluidseparation between the aft channel and the other channels of the leadingedge cavity.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises a leading edge feed aperture atan inner diameter end thereof, the leading edge feed aperture configuredto direct a cooling flow into the showerhead radial channel at an innerdiameter end thereof.

In addition to one or more of the features described above, or as analternative, further embodiments of the airfoil assemblies may includethat the leading edge baffle comprises at least one side feed aperturearray at an inner diameter end thereof, the at least one side feedaperture array configured to direct a cooling flow into at least one ofthe pressure side radial flow channel or the suction side radial flowchannel at an inner diameter end thereof.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation thereof will becomemore apparent in light of the following description and the accompanyingdrawings. It should be understood, however, the following descriptionand drawings are intended to be illustrative and explanatory in natureand non-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

The following descriptions should not be considered limiting in any way.With reference to the accompanying drawings, like elements are numberedalike: The subject matter is particularly pointed out and distinctlyclaimed at the conclusion of the specification. The foregoing and otherfeatures, and advantages of the present disclosure are apparent from thefollowing detailed description taken in conjunction with theaccompanying drawings in which like elements may be numbered alike and:

FIG. 1 is a schematic cross-sectional illustration of a gas turbineengine;

FIG. 2 is a schematic illustration of a portion of a turbine section ofthe gas turbine engine of FIG. 1 ;

FIG. 3A is an axial cross-section schematic illustration of an airfoil;

FIG. 3B is a cross-sectional illustration of the airfoil of FIG. 3A asviewed along the line B-B of FIG. 3A;

FIG. 4A is a schematic illustration of an airfoil assembly having anairfoil body and a baffle in accordance with an embodiment of thepresent disclosure;

FIG. 4B is a side elevation view of the baffle of FIG. 4A;

FIG. 4C is a side elevation view of the structure of the airfoil body ofFIG. 4A;

FIG. 4D is an enlarged illustration of features of the airfoil assemblyof FIG. 4A;

FIG. 5 is a schematic illustration of a baffle in accordance with anembodiment of the present disclosure;

FIG. 6 is a schematic illustration of baffle in accordance with anembodiment of the present disclosure;

FIG. 7A is a schematic illustration of a baffle in accordance with someembodiments of the present disclosure;

FIG. 7B is a cross-sectional view of the baffle of FIG. 7B;

FIG. 7C is an enlarged schematic illustration of the baffle of FIG. 7Aas installed within an airfoil body;

FIG. 8 is a schematic illustration of a baffle and airfoil body inaccordance with an embodiment of the present disclosure;

FIG. 9A is a side elevation view of a baffle in accordance with anembodiment of the present disclosure;

FIG. 9B is a side elevation view of the structure of an airfoil havingthe baffle of FIG. 9A installed therein;

FIG. 10A is a schematic illustration of a baffle installed in an airfoilin accordance with an embodiment of the present disclosure; and

FIG. 10B is an enlarged illustration of the configuration of FIG. 10A.

DETAILED DESCRIPTION

Detailed descriptions of one or more embodiments of the disclosedapparatus and/or methods are presented herein by way of exemplificationand not limitation with reference to the Figures.

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. The fan section 22 drivesair along a bypass flow path B in a bypass duct, while the compressorsection 24 drives air along a core flow path C for compression andcommunication into the combustor section 26 then expansion through theturbine section 28. Although depicted as a two-spool turbofan gasturbine engine in the disclosed non-limiting embodiment, it should beunderstood that the concepts described herein are not limited to usewith two-spool turbofans as the teachings may be applied to other typesof turbine engines.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided, and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 and a low pressureturbine 46. The inner shaft 40 is connected to the fan 42 through aspeed change mechanism, which in exemplary gas turbine engine 20 isillustrated as a geared architecture 48 to drive the fan 42 at a lowerspeed than the low speed spool 30. The high speed spool 32 includes anouter shaft 50 that interconnects a high pressure compressor 52 and highpressure turbine 54. A combustor 56 is arranged in exemplary gas turbine20 between the high pressure compressor 52 and the high pressure turbine54. An engine static structure 36 is arranged generally between the highpressure turbine 54 and the low pressure turbine 46. The engine staticstructure 36 further supports bearing systems 38 in the turbine section28. The inner shaft 40 and the outer shaft 50 are concentric and rotatevia bearing systems 38 about the engine central longitudinal axis Awhich is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The turbines 46, 54 rotationally drive therespective low speed spool 30 and high speed spool 32 in response to theexpansion. It will be appreciated that each of the positions of the fansection 22, compressor section 24, combustor section 26, turbine section28, and fan drive gear system 48 may be varied. For example, gear system48 may be located aft of combustor section 26 or even aft of turbinesection 28, and fan section 22 may be positioned forward or aft of thelocation of gear system 48.

The engine 20 in one non-limiting example is a high-bypass gearedaircraft engine. In a further non-limiting example, the engine 20 bypassratio is greater than about six (6), with an example embodiment beinggreater than about ten (10), the geared architecture 48 is an epicyclicgear train, such as a planetary gear system or other gear system, with agear reduction ratio of greater than about 2.3 and the low pressureturbine 46 has a pressure ratio that is greater than about five. In onedisclosed embodiment, the engine 20 bypass ratio is greater than aboutten (10:1), the fan diameter is significantly larger than that of thelow pressure compressor 44, and the low pressure turbine 46 has apressure ratio that is greater than about five 5:1. Low pressure turbine46 pressure ratio is pressure measured prior to inlet of low pressureturbine 46 as related to the pressure at the outlet of the low pressureturbine 46 prior to an exhaust nozzle. The geared architecture 48 may bean epicycle gear train, such as a planetary gear system or other gearsystem, with a gear reduction ratio of greater than about 2.3:1. Itshould be understood, however, that the above parameters are onlyexemplary of one embodiment of a geared architecture engine and that thepresent disclosure is applicable to other gas turbine engines includingdirect drive turbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,688 meters). The flight condition of 0.8 Mach and35,000 ft (10,688 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption TSFC′)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The lowfan pressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.45. “Low corrected fan tip speed” is theactual fan tip speed in ft/sec divided by an industry standardtemperature correction of [(Tram ° R)/(514.7° R)]^(0.5). The “Lowcorrected fan tip speed” as disclosed herein according to onenon-limiting embodiment is less than about 1150 ft/second (350.5 m/sec).

Although the gas turbine engine 20 is depicted as a turbofan, it shouldbe understood that the concepts described herein are not limited to usewith the described configuration, as the teachings may be applied toother types of engines such as, but not limited to, turbojets,turboshafts, etc.

Referring now to FIG. 2 , a cooling design in a turbine section 28 for agas turbine engine 20 may utilize a vane 106 disposed between axiallyadjacent bladed full hoop disks 108, 108 a having respective blades 109,109 a. As shown, vane 106 is disposed radially between an inner air seal112 and a full hoop case 114 on an outer side. Inner air seal 112 may bea full hoop structure supported by opposing vanes, including a pluralityof vanes 106 that are separated in a circumferential direction. Vane 106is supported by the full hoop case 114 through segmented vane hooks 117,117 a. One or more full hoop cover plates 115, 115 a may minimizeleakage between the vane 106 and the blades 109, 109 a. The vane 106 isradially supported by the full hoop case 114 with segmented case hooks116, 116 a in mechanical connection with the segmented vane hooks 117,117 a. The vane 106 may be circumferentially supported betweencircumferentially adjacent platforms 119, 119 a which may includefeather seals that can minimize leakage between the adjacent vanes 106into the gas path.

Although FIG. 2 depicts a second stage vane, as appreciated by those ofskill in the art, embodiments provided herein can be applicable to firststage vanes as well. Such first stage vanes may have cooling flowsupplied to the vane at both the inner and outer diameters, as opposedto the through-flow style cavity which goes from, for example, outerdiameter to inner diameter. Thus, the present illustrations are not tobe limiting but are rather provided for illustrative and explanatorypurposes only.

In the present illustration, a turbine cooling air (TCA) conduit 125provides cooling air into an outer diameter vane cavity 124 defined inpart by an outer platform 119 and the full hoop case 114. The vane 106is hollow so that air can travel radially into and longitudinallydownstream from the outer diameter vane cavity 124, through the vane 106via one or more vane cavities 122, and into a vane inner diameter cavity123. The vane inner diameter cavity 123 is defined, in part, by an innerplatform 119 a. Thereafter air may travel through an orifice 120 in theinner air seal 112 and into a rotor cavity 121. Accordingly, cooling airfor at least portions of the vane 106 will flow from a platform region,into the vane, and then out of the vane and into another platform regionand/or into a hot gaspath/main gaspath. In some arrangements, the vane106 and/or the platforms 119, 119 a may include ejection holes to enablesome or all of the air to be injected into the main gaspath.

It is to be appreciated that the longitudinal orientation of vane 106 isillustrated in a radial direction, but other orientations for vane 106are within the scope of the disclosure. In such alternate vaneorientations, fluid such as cooling air can flow into the vane cavity122 through an upstream opening illustrated herein as outer diametercavity 124 and out through a downstream opening in the vane cavity 122illustrated herein along a longitudinal span of the vane cavity 122being between such openings, as well as out through a downstream cavityand/or manifold (e.g., vane inner diameter cavity 123).

The vane 106, as shown, includes one or more baffles 126 located withinthe vane 106. The baffles 126 are positioned within one or morerespective baffle cavities 128. The baffle cavities 128 are sub-portionsor sub-cavities of the vane cavity 122. In some embodiments, such asshown in FIG. 2 , the baffle cavities 128 are internal cavities that areaxially inward from the leading and trailing edges of the vane 106,although such arrangement is not to be limiting. The TCA conduit 125 mayprovide cooling air that can flow into the baffles 126 and then impingefrom the respective baffle 126 onto an interior surface of the vane 106.In some embodiments, a leading edge cavity (e.g., a vane cavity 122) maybe configured as a single flow-through cavity, with cooling flow flowingfrom the outer diameter vane cavity 124, through the leading edge cavity(providing cooling to the vane), and then into the inner diameter cavity123. Aft of the leading edge cavity may be one or more main bodycavities which may be through-flow cavities or arranged as a serpentinecavity that exits through a trailing edge of the vane 106.

As shown and labeled in FIG. 2 , a radial direction R is upward on thepage (e.g., radial with respect to an engine axis) and an axialdirection A is to the right on the page (e.g., along an engine axis).Thus, radial cooling flows will travel vertically/radially up or down onthe page and axial flows will travel horizontally/axially left-to-right(or vice versa). A circumferential direction C is a direction into andout of the page about the engine axis.

Turning now to FIGS. 3A-3B, schematic illustrations of an airfoil 300having a mid-cavity baffle 302 and a leading edge cavity baffle 304installed therein are shown. Each baffle 302, 304 has a baffle body thatdefines the structure and shape of the respective baffle 302, 304. Theairfoil 300 extends in an axial direction between a leading edge 306 anda trailing edge 308. In a radial direction, the airfoil 300 extendsbetween an inner platform 310 at an inner diameter 312 and an outerplatform 314 at an outer diameter 316. In this illustrative embodiment,the airfoil 300 has three internal cavities: a leading edge cavity 318,a mid-cavity 320, and a trailing edge cavity 322. Although shown with aspecific cavity configuration, those of skill in the art will appreciatethat airfoils can have a variety of internal cavity configurations andimplement embodiment of the present disclosure. Thus, the presentillustration is merely for explanatory purposes and is not to belimiting. FIG. 3A is an axial cross-section illustration of the airfoil300 illustrating an internal structure thereof. FIG. 3B is across-sectional illustration as viewed along the line B-B. It will beappreciated by those of ordinary skill in the art that a typicalmetallic airfoil (e.g., Ni-base airfoil) will include internal featuressuch as trip strips, pin fins, pedestals, hemispherical bumps, deltafins, or other types of heat transfer augmentation features cast intothe interior wall surfaces of internal cavities and/or the insertedbaffles include impingement holes for enabling impinging air to cool theinterior surfaces of the airfoil.

One or more of the cavities 318, 320, 322 may be separated by rib 324with fluid connections therebetween in some embodiments. The rib 324extends radially between the inner platform 310 at the inner diameter312 to the outer platform 314 at the outer diameter 316. A first rib 324may separate the mid-cavity 320 from the leading edge cavity 318, andmay, in some embodiments, fluidly separate the two cavities 318, 320. Asecond rib may separate the mid-cavity 320 from the trailing edge cavity322, and may, in some embodiments, have through holes to fluidly connectthe mid-cavity 320 to the trailing edge cavity 322. In some embodiments,the cavities 318, 320, 322 may include one or more heat transferaugmentation features, such as trip strips, pedestals, pin fins, etc.included in the airfoil body (i.e., cast in) and/or attached to theinterior wall surfaces.

In this embodiment, the leading edge cavity 318 includes a leading edgecavity baffle 304 installed therein and the mid-cavity 320 includes amid-cavity baffle 302 therein. The mid-cavity baffle 302 includesmid-cavity baffle apertures 326 (shown in FIG. 3B) to supply cooling airfrom within the mid-cavity baffle 302 into the mid-cavity 320. Thecooling air within the mid-cavity 320 may flow into the trailing edgecavity 322 and subsequently exit the airfoil 300 through a dischargeslot of the trailing edge 308. Such discharge slot of the trailing edge308 may include various internal cooling features to provide anappropriate air flow distribution in order to provide adequate thermalcooling effectiveness in order to achieve local metal temperature,durability life, and aerodynamic performance characteristics. Theleading edge cavity baffle 304 includes leading edge cavity baffleapertures 328 where cooling air within the leading edge cavity baffle304 may impinge upon surfaces of the airfoil 300 of the leading edgecavity 318. The cooling or impinged air may then exit the leading edgecavity 318 through film cooling apertures 330, as will be appreciated bythose of skill in the art.

Embodiments of the present disclosure are directed to optimization ofheat transfer within a vane by minimizing cross-sectional area andproviding cooling to the hottest area of the airfoil, namely the airfoilleading edge, as well as the airfoil pressure side surface and theairfoil suction side surface. This is especially useful for later stageairfoils that may not be supplied with high enough flow allotments foradequate cooling or pressure levels that may exist in more typicalconfigurations. Embodiments of the present disclosure are directed tocombining a space-eater baffle with cast-in standoff features of a vaneto create multiple radial extending channels. The radial extendingchannels may be supplied with cooling air that enters the vane fromeither the outer diameter or the inner diameter of the airfoil. Thiscooling flow may be bled into a showerhead region of the vane and/orpassed through the baffle (or vane) to feed an inner diameter platformor downstream components. The flow-bleed functionality is a product ofthe use of pedestal standoffs of the airfoil which mate up against thebaffle during operation in order to control the rate of migration of theflow from radially partitioned channels into the showerhead region tothen dump the flow into the gas-path. Embodiments of the presentdisclosure provide a robust vane cooling configuration with cast-infeatures and impingement feeds that are drilled into the baffle. Theimpingement feeds can be tailored to address high heat-load areas, forexample.

In certain engine and/or airfoil configurations, flow allotment andpressure levels may not allow for traditional leading edge coolingconfigurations (e.g., peanut cavity and/or impingement baffle). Forexample, in some non-limiting engine configurations, a second stage vaneassembly (i.e., aft of a first stage vane assembly) may receive aboutone third or less of the amount of cooling flow extracted for the firststage vane assembly. As such, the first stage vane assembly may employconventional impingement baffles due to the high flow level. However,the lower amount of cooling flow at the downstream second stage vaneassembly may require additional features because pure impingementcooling configurations may not be viable due to the lower flow levels atthe second stage (aft) vane assembly.

Additionally, structural concerns may require a vane structure thatmaximizes the distance between the leading edge and the first rib withinthe airfoil (e.g., forming a large axial extent leading edge cavity). Inorder to optimize heat transfer in such airfoils, a radially flowingspace-eater baffle is implemented in conjunction with standoffs that areformed on the interior walls of the airfoil body. The baffle enablesoptimization of channel cooling flow area (in the flow direction) inlieu of using cast-in ribs and the radial (rather than axial) floworientation further reduces the overall cross-sectional area that drivesheat transfer. The radially extending standoffs of the airfoil may beused to segregate cooling channels in a way that optimizes heattransfer. Such cooling channels are defined between an exterior surfaceof the baffle and an interior surface (e.g., hot wall) of the airfoilbody.

The use of unique pedestal standoffs can be employed to bleed flow to ashowerhead region to feed cooling holes of the airfoil. Pedestal bleedarea distribution can be tailored such that heat transfer requirementsare met both in the radial channel (s) and a showerhead region of theairfoil. In some embodiments, baffle resupply holes can be added toaddress specific areas of high heat-load, introducing impingementcooling while pedestals manage the rate at which the cooler air migratesto and mixes in the showerhead region. Baffle impingement feeds can betailored to optimize heat transfer and fill characteristics of theradial channel(s).

Additionally, a number of impingement holes may be utilized on thecold-rib side of the baffle (e.g., aft-facing) to create a fluidic wall,discouraging communication between pressure side and suction sidechannels along the aft portion of the leading edge cavity.

Turning now to FIGS. 4A-4D, schematic illustrations of an airfoilassembly 400 in accordance with an embodiment of the present disclosureare shown. The airfoil assembly 400 includes an airfoil body 402 and aleading edge baffle 404 installed within a leading edge cavity 406 ofthe airfoil body 402. FIG. 4A is a cross-sectional view of the airfoilassembly 400, FIG. 4B is a side elevation view of the leading edgebaffle 404, FIG. 4C is a schematic illustration of the interiorstructure of the airfoil body 402 of the airfoil assembly 400, and FIG.4D is a schematic illustration of the interior structure of the airfoilbody 402 within the leading edge cavity 406.

The leading edge baffle 404 is arranged within the leading edge cavity406. The leading edge cavity 406 is an enlarged leading edge cavity. Forexample, and in accordance with some embodiments of the presentdisclosure and without limitation, an axial length of the leading edgecavity 406 may extend at least 20% of the axial distance of the airfoilbetween a leading edge and a trailing edge thereof. In some non-limitingconfigurations, the axial length of the leading edge cavity 406 may bebetween 20% and 70% of the axial length of the airfoil (from leadingedge to trailing edge). This increased distance (e.g., as compared toprior configurations having a profile in the axial direction of lessthan 20%) allows for an improved cooling scheme of the airfoil, whencombined with the other features described. The leading edge cavity 406is sized to accommodate installation of the leading edge baffle 404 intothe airfoil.

Such an enlarged leading edge cavity 406 increases the distance betweena leading edge 408 of the airfoil body and an interior rib 410 of theairfoil body 402. The leading edge cavity 406 is defined at a forwardend by the leading edge 408 and at an aft end by the interior rib 410.Sides of the leading edge cavity 406 are defined by a pressure side wall412 and a suction side wall 414 of the airfoil body 402. Of the walls orsurfaces that define the leading edge cavity 406, the leading edge 408,the pressure side wall 412, and the suction side wall 414 are “hotwalls” that are exposed to hot gases or the hot gas path when inoperation. The interior rib 410 is a “cold wall” that does not havesurfaces that are directly exposed to hot gas during operation.

To position the leading edge baffle 404 within the leading edge cavity406, the airfoil body 402 includes a number of radially extendingstandoff rails 416, 418 that extend inward from the respective walls ofthe leading edge cavity 406. As used herein, the term “radial” refers toa direction when installed within an engine, such that radial isinto/out of the page in FIG. 4A and up/down in FIGS. 4B-4C. As shown,the airfoil body 402 includes two forward radially extending standoffrails 416 a, 416 b and two aft radially extending standoff rails 418 a,418 b. A first forward radially extending standoff rail 416 a and afirst aft radially extending standoff rail 418 a are arranged along thepressure side wall 412. A second forward radially extending standoffrail 416 b and a second aft radially extending standoff rail 418 b arearranged along the suction side wall 414.

When the leading edge baffle 414 is arranged within the leading edgecavity 406, the leading edge cavity 406 is divided into a number ofsub-cavities and/or channels. For example, with reference to FIG. 4A, afeed cavity 420 is defined within the interior of the leading edgebaffle 404. In some embodiments, the feed cavity 420 may be athrough-flow cavity that extends between open ends at the inner andouter diameter ends of the leading edge baffle 406 (in a radialdirection). In other embodiments, the inner diameter end of the leadingedge baffle 404 may be capped such that the leading edge baffle 404 actsas a plenum to supply cooling air into various channels defined betweenthe exterior surface of the leading edge baffle 404 and an interiorsurface of the airfoil body 402.

A showerhead radial channel 422 is defined between the interior surfaceof the leading edge cavity 404, an exterior surface of the leading edgebaffle 404, and between the first and second forward radially extendingstandoff rails 416 a, 416 b. A pressure side radial flow channel 424 isdefined between the pressure side wall 412, an exterior surface of theleading edge baffle 404, the first forward radially extending standoffrail 416 a, and the first aft radially extending standoff rail 418 a. Asuction side radial flow channel 426 is defined between the suction sidewall 414, an exterior surface of the leading edge baffle 404, the secondforward radially extending standoff rail 416 b, and the second aftradially extending standoff rail 418 b. An aft channel 428 is definedaft of each of the first and second aft radially extending standoffrails 418 a, 418 b along the pressure and suction side walls 412, 414,the interior rib 410 of the airfoil body 402, and exterior surfaces ofthe leading edge baffle 404. The aft channel 428 may be a through-flowchannel that is open at an inner diameter end to supply cooling air, forexample, to an inner diameter platform or other downstream components orcavities of an engine structure.

FIG. 4B illustrates a side elevation view (pressure side) of the leadingedge baffle 404. The leading edge baffle 404 extends radially between anouter diameter end 430 to an inner diameter end 432. In someembodiments, each of the outer diameter end 430 and the inner diameterend 432 may be open or unobstructed to allow airflow therethrough. Inother embodiments, the leading edge baffle 404 may be capped at theinner diameter end 432 to form a plenum to supply cooling flow into thechannels external to the leading edge baffle 404. As shown, the leadingedge baffle 404 includes a number of feed apertures 434, 436, 438located proximate an inlet end of the leading edge baffle 404 (in thiscase, the outer diameter end 430). The leading edge baffle 404 will befed with cooling air from a platform or other source, as known in theart, and the cooling air will enter the feed cavity 420 and flow intothe channels 422, 424, 426, 428 defined between the exterior of theleading edge baffle 404 and the interior surfaces of the airfoil body402.

A leading edge feed aperture 434 is arranged on a leading edge end ofthe leading edge baffle 404 and is configured to supply cooling air intothe showerhead radial channel 422. The flow through the leading edgefeed aperture 434 will enter the showerhead radial channel 422, from thefeed cavity 420, at the outer diameter thereof and then flow radiallyinward (downward) along the interior surface of the leading edge 408 ofthe airfoil body 402. The cooling flow will then exit through one ormore showerhead apertures 440 which may expel cooling flow along theexterior of the leading edge 408 of the airfoil body 402 and providefilm cooling thereto.

Each of the pressure side radial flow channel 424 and the suction sideradial flow channel 426 may be fed with cooling flow through respectivepressure and suction side feed aperture arrays 436 (pressure side shownin FIG. 4B with a similar array on the suction side). The cooling flowwill enter the feed cavity 420 and pass through the side feed aperturearrays 436 to enter the respective channels 422, 424 and flow radiallyinward (toward the inner diameter end 432) to provide cooling to theforward portions of each of the pressure side wall 412 and the suctionside wall 414 of the leading edge cavity 406.

The aft channel 428 may be supplied with cooling from through aft feedaperture arrays 438 (e.g., an array on each of the pressure and suctionsides of the leading edge baffle 404). The cooling flow will enter thefeed cavity 420 and pass through the aft feed aperture arrays 438 toenter the aft channel 428 and flow radially inward (toward the innerdiameter end 432) to provide cooling to the aft portions of each of thepressure side wall 412 and the suction side wall 414 of the leading edgecavity 406.

Feed aperture arrays in accordance with embodiments of the presentdisclosure can be adjusted/tailored to optimize fill characteristics andimpingement heat transfer. The feed aperture arrays may serve todistribute flow between channels as desired. For example, the total areaof the feed array for the forward suction side channel may be greaterthan any other channel due to requiring a larger amount of flow to coolthe forward suction side gas path surfaces of the airfoil. Flow splitsbetween channels can allow for further optimization/adjustment if hotspots are noticed and flow can be spared from another channel to addresssuch hot spots.

As shown in FIG. 4B, the leading edge baffle 404 has a substantiallysolid wall with no apertures or openings defined by a solid portion 442that extends radially from a lower extent of the feed apertures 434,436, 438 to the inner diameter end 432 of the leading edge baffle 404.The solid portion 442 of the leading edge baffle 404 provides forsurface along which the cooling flow will pass and can pick up heatwithout significant disruption. In addition to providing a coolingchannel of the desired size, less temperature increase may be realizedin the cooling air when using a space-eater baffle in accordance withembodiments of the present disclosure. Traditional cooling channels havethe air sandwiched between two alloy walls and thus pick up heat basedon the temperature contribution on both the pressure side and suctionside. However, in accordance with embodiments of the present disclosure,by using a space-eater baffle, the heat pickup may be reduced to half asthe baffle wall temperature is essentially equal to the coolanttemperature. This makes for more effective cooling in general as theheat transfer is directly related to the difference in temperaturebetween the alloy wall and the coolant.

The solid portion 442 may define, for example at least 75% of the radialheight of the leading edge baffle 404. In other embodiments, the solidportion 442 may define about 50% of the radial height of the leadingedge baffle 404. As such, it will be appreciated that the radial heightof the solid portion may be selected based on specific cooling schemesand requirements for the particular airfoil and/or location within a gasturbine engine. It should be noted that leading edge baffle 404 mayinclude flow apertures the may extend radially, either periodically,intermittently or in a pattern, from the outer diameter end 430 to theinner diameter end 432 to mitigate pressure loss and cooling airtemperature heat pickup to address local back flow margin and/or achievelocal thermal cooling effectiveness requirements to nonuniformities inthe radial gas temperature profile.

The aft channel 428 may be substantially fluidly separate from theforward positioned side radial flow channels 424, 426. Such fluidseparation may be provided by the aft radially extending standoff rails418 a, 418 b, as shown in FIGS. 4A, 4C. Because the aft channels arefluidly separate from the forward channels, each section can beaddressed individually to meet the cooling required for their respectiveheat loads without risk of unexpected cooling imbalance when one or theother is adjusted. In some embodiments, the aft radially extendingstandoff rails 418 a, 418 b may be solid from a position proximate theouter diameter end 430 to a position proximate the inner diameter end432 when viewed relative to the leading edge baffle 404. In someembodiments, however, one or more cross-over holes may be arranged inthe aft radially extending standoff rails 418 a, 418 b to permit someamount of fluid communication between the side radial flow channels 424,426 and the aft channel 428.

The aft radially extending standoff rails 418 a, 418 b and the forwardradially extending standoff rails 416 a, 416 b define the side radialflow channels 424, 426 therebetween. However, unlike the aft radiallyextending standoff rails 418 a, 418 b, the forward radially extendingstandoff rails 416 a, 416 b are defined as interrupted or segmentedrails. The segmented nature of the forward radially extending standoffrails 416 a, 416 b permits cooling from within the side radial flowchannels 424, 426 to flow into the showerhead radial channel 422. Suchflow may be a resupply flow that provides cooling flow to radial inwardportions of the showerhead radial channel 422 along the leading edge 408of the airfoil body 402, as needed. In other configurations, the flowaperture openings may be tailored to redistribute flow may be customizedas needed to optimize allotted cooling flow to achieve desired localthermal cooling performance. For example, more flow can be distributednear the outer diameter, if needed, or most of the flow may be keptwithin the channel and combined at the inner diameter, or combinationsthereof.

The flow apertures created between the leading edge baffle 404 and theforward radially extending standoff rails 416 a, 416 b may be varied inboth size and shape. The resulting flow geometry of the apertures may bedefined by a flat edge formed by an exterior surface of the leading edgebaffle 404 and a filleted blend surface that is formed by the radiallyextending interrupted or segmented forward radially extending standoffrails 416 a, 416 b. The aspect ratio of the formed apertures may rangebetween 1:1≥W/H≥10:1, depending on flow and pressure loss requirements.The flow aperture geometry may approximate a circle, an oblong, and/oran elliptical shape/geometry, recognizing that the one side of theaperture created by the leading edge baffle 404 will generally be planaror have a slight amount of curvature depending on the local airfoil andbaffle radius curvature. It is noted that axial flow apertures may beprovided to generate local convective heat transfer immediately adjacentto the hot wall. Subsequent to the radially distributed flow aperturesin the segmented standoff rails 416 a, 416 b, trip strip or othersimilar features may be incorporated into or on surfaces of theshowerhead radial channel 422 to further enhance the local convectiveheat transfer and improve local thermal cooling performance. It is alsonoted that while the current illustrations show apertures in in thesegmented standoff rails 416 a, 416 b, it will be appreciated that thesegmented apertures can be offset from the hot wall to simulate more ofan impingement rib-type of effect.

The leading edge baffle 404 is positioned and retained within theleading edge cavity 406 by the radially extending standoff rails 416,418 and an inner diameter forward collar 444. The inner diameter forwardcollar 444 is a structural feature of the airfoil body 402. The innerdiameter forward collar 444 extends from an inner diameter end of eachof the aft radially extending standoff rails 418 a, 418 b in a forwarddirection toward the leading edge 408 of the airfoil body 402, as shownin FIGS. 4C-4D. As shown, the inner diameter forward collar 444 mayprovide for an inner diameter wall or blockage, which preventsthroughflow of the cooling air through the side radial flow channels424, 426 and/or the showerhead radial channel 422. This results in theair within such channels 422, 424, 426, 428 to be expelled through theshowerhead apertures 440 and keeps this portion of the airfoil fluidlyseparate from the inner diameter platform and aft leading edge regions.In some embodiments, the leading edge baffle 404 may rest, at leastpartially, upon the inner diameter forward collar 444.

Although not illustrated, a similar collar may also be incorporated atthe outer diameter end 430 of the airfoil assembly 400. The utilizationof a collar at the outer diameter end 430 of the airfoil assembly 400may be twofold. For example, such an outer diameter collar may allow forcircumferential positioning of the leading edge baffle 404.Additionally, such an outer diameter collar may provide support tomitigate potential deflection of the leading edge baffle 404 duringmanufacturing and/or assembly. Further, for example, the incorporationof an outer diameter collar may mitigate potential bulging of the bafflewalls that may occur during engine operation due to a pressure gradientthat exist between the inner baffle cavity 420 and the baffle gapchannels 422, 424, 426, 428.

As such, the incorporation of collars may mitigate baffle deformationduring assembly and/or during engine operation. Further, one or morediscrete standoff features may be provided to maintain a design intentradial baffle gap height and channel flow area to achieve desiredpressure loss and heat transfer characteristics and achieve thermalcooling performance requirements. The discrete standoff features mayeither be cast features and/or integrated into the leading edge baffle404 design coincident with predicted baffle deformation locations atdetermined radial and/or circumferential locations.

Such outer diameter collar may be a continuous feature (e.g., solid) ormay be perforated (e.g., apertures, holes, openings, or otherwisediscontinuous) with at least one flow aperture to provide additionalcooling flow to the radial baffle gap channels 422, 424, 426, 428. Theouter diameter collar may be flush with the outer diameter end 430 ofthe airfoil assembly 400 or may extend radially outward beyond the outerdiameter end 430. As such, at least one flow aperture within the outerdiameter collar may be oriented either horizontally or radially to serveas conduit for outer diameter platform cooling flow to improve backsideplatform convective heat transfer characteristics.

As noted above, such an outer diameter collar may also contain at leastone radial oriented aperture to further increase a cooling flow rate inthe radial baffle gap channels 422, 424, 426, 428, to increase localbackside convective cooling and/or increase radial baffle gap channelpressures for incorporation of film cooling if required. Additionally,an outer diameter baffle flange may be integrated with the leading edgebaffle 404 to provide similar positioning (e.g., circumferentialpositioning) and allowance for at least one cooling flow aperture tooptimize and tailor internal radial baffle gap cooling flow and pressuredistribution within the channels 422, 424, 426, 428.

As shown in FIG. 4C, the interior surface of the airfoil body 402 mayinclude heat transfer augmentation features 446 distributed alongsurfaces of the channels 422, 424, 426, 428. The heat transferaugmentation features 446 may be trip strips, chevron strips, pedestals,pin fins, hemispherical bumps, delta fins, or other internal surfacefeatures that are configured to control and/or direct flow to ensurecooling of the material of the airfoil body 402.

The airfoil assembly 400 includes the aft radially extending standoffrails 418 a, 418 b that segregates the aft channel 428 from the sideradial flow channels 424, 426 in a way that optimizes heat transfer.Further, the segmented forward radially extending standoff rails 416 a,416 b enable bleed flow from the side radial flow channels 424, 426 tothe showerhead radial channel 422 to feed cooling holes (e.g.,showerhead apertures 440).

In some embodiments, the airfoil assembly 400 may be arranged as asecond stage vane within a turbine or compressor section of a gasturbine engine. The second stage vane may require unique coolingsolutions due to the downstream position relative to a first stage vane.As noted above, this is due to the fact that the first stage vane heatloads are greater and thus the first stage vane receives a much largeramount of the available cooling air. Similarly, blade cooling allotmentsare higher as they are rotating as such additional considerationsassociated with airfoil creep and thermal mechanical fatigue must beaddressed. However, in accordance with embodiments of the presentdisclosure, less flow may be used efficiently in downstream (e.g.,second stage or aft positioned vanes) in order to achieve life metrics.Because of this, the use of the described leading edge baffle canoptimize the cooling of the leading edge of the second stage vane andthus improve part life and operational temperatures.

Turning now to FIG. 5 , a schematic illustration of a leading edgebaffle 500 in accordance with an embodiment of the present disclosure isshown. The leading edge baffle 500 may be installed within a leadingedge cavity of an airfoil body (not shown), similar to that shown anddescribed above with respect to FIGS. 4A-4D. The leading edge baffle 500may be configured to be positioned with such leading edge cavity of theairfoil and retained therein by one or more radial standoff rails. Forexample, as shown in phantom lines, a forward rail 502 and an aft rail504 are shown relative to the leading edge baffle 500. The forward rail502 may be a segmented rail similar to the forward radially extendingrails 416 a, 416 b and the aft rail 504 may be solid rail similar to theaft radially extending rails 418 a, 418 b.

Similar to the leading edge baffle 404 described above, the leading edgebaffle 500 extends in a radial direction between an outer diameter end506 and an inner diameter end 508. The leading edge baffle 500 may havean opening or open end at the outer diameter end 506 and may be closed,capped, or otherwise sealed at the inner diameter end 508. Proximate theouter diameter end 506 of the leading edge baffle 500 are a leading edgefeed aperture 510, side feed aperture arrays 512, and aft feed aperturearrays 514, similar to that described above. Radially inward from thefeed apertures 510, 512, 514, the leading edge baffle 500 includes asolid portion 516. However, in this embodiment, the solid portion 516includes resupply apertures 518 arranged between the lowest extent (inthe radial direction) of the feed apertures 510, 512, 514 and the innerdiameter end 508 of the leading edge baffle 500. In this embodiment, theresupply apertures 518 are arranged on the portion of the leading edgebaffle 500 that defines the side radial flow channels (i.e., not the aftchannel nor the showerhead radial channel) and illustrated between theforward rail 502 and an aft rail 504 when installed within an airfoil.The resupply apertures 518 may be provided to target area(s) of lowstatic pressure, high heat loads, and/or to increase fill and generalcooling within the radial channels.

Turning now to FIG. 6 , a schematic illustration of a leading edgebaffle 600 in accordance with an embodiment of the present disclosure isshown. The leading edge baffle 600 may be substantially similar to thatshown and described above. The view of FIG. 6 is a forward facing viewof an aft wall 602 of the leading edge baffle 600. The aft wall 602 ofthe leading edge baffle 600 is configured to face an internal rib of anairfoil in which the leading edge baffle 600 is installed (e.g.,interior rib 410 of the airfoil body 402 shown in FIG. 4A). The leadingedge baffle 600 includes one or more trailing edge impingement apertures604 formed in the aft wall 602. These apertures 604 can also take theform of various slot configurations along each respective row.Additionally, the apertures are not limited to two discrete and/or equalrows as shown, but rather variations or unequal distributions may beemployed. Further, for example, the apertures could be placed down thecenter of the baffle, or in other arrays, with the aperture areaadjusted as needed to create a fluidic wall as desired. The trailingedge impingement apertures 604 are configured to impinge cooling flowfrom the interior of the leading edge baffle 600 toward an interior ribof the airfoil body. The impinging flow can prevent cross-flow or flowmigration between the pressure and suction sides of the aft channel.

As discussed above, the described leading edge baffles may be positionedwithin a leading edge cavity and supported, at least in part, by theradial rails and/or collar. In some embodiments, the leading edgebaffles may rely on cast-in standoffs (e.g., radial rails) mating upwith the sheet metal in operation in order to create segregated channelsand control flow fields, as described above. When installed/assembled,there must be a gap left between the standoff rails and the exteriorsurface of the leading edge baffle such that insertion of the baffle ispossible within the leading edge cavity. The gap can increase if thereis significant curvature in the airfoil, leading to scenarios where thecold-state finished assembly has larger than desired gaps between theexterior baffle surfaces and stand-off rails. In operation, some amountof baffle bulge is expected, though it is difficult to predict theamount of bulge for any given operating point, thus the smaller the gapsin the areas requiring high heat transfer in the cold-state the better.

To accommodate such considerations the leading edge baffles of thepresent disclosure may include a “negative” bump-in, depression, groove,recess, etc. (hereinafter referred to as a “standoff shelf”) atlocations that will mate or align with the radial rails/standoffs. Byincluding such standoff shelves, the sheet metal baffle around theradial rails can allow the material surfaces of the baffle defining theradial channels to sit closer (in the cold-state) to the interiorsurface of the airfoil body walls (e.g., leading edge, pressure sidewall, suction side wall) than it otherwise would have without suchstandoff shelves. The standoff shelves may run the entire (radial)length of the respective radial rail to which the standoff shelf mayengage. Such standoff shelves may increase the confidence that thechannel heights used in analysis are not disrupted due to gappingrequired at the radial rails. Gaps around the radial rails can beminimized, but with these features, there would be no collateral damagedone to the height of the heat transfer channels defined between theexterior of the leading edge baffle and the interior surfaces of theairfoil body.

Turning now to FIGS. 7A-7C, schematic illustrations of a leading edgebaffle 700 in accordance with an embodiment of the present disclosureare shown. FIG. 7A is a pressure side elevation view of the leading edgebaffle 700, FIG. 7B is a cross-sectional view looking radially inward atthe line B-B shown in FIG. 7A, and FIG. 7C is an enlarged detailed viewof the leading edge baffle 700 as installed within an airfoil body 702.The leading edge baffle 700 may be substantially similar to that shownand described above, being configured to be installed within a leadingedge cavity of an airfoil and define multiple radial flow channelsbetween the exterior of the leading edge baffle 700 and the interiorsurfaces of the leading edge cavity.

As shown in FIG. 7A, the leading edge baffle 700 includes a baffle body704 that extends radially between an outer diameter end 706 and an innerdiameter end 708. On the exterior surface of the leading edge baffle700, a number of standoff shelves 710, 712 are formed within thematerial of the leading edge baffle 700. Forward standoff shelves 710(710 a, 710 b shown in FIG. 7B) are arranged at a forward end of theleading edge baffle 700 and are configured to engage with forwardradially extending rails of an airfoil body (e.g., forward radiallyextending rails 416 a, 416 b). Aft standoff shelves 712 (712 a. 712 bshown in FIG. 7B) are arranged aft of the forward standoff shelves 710and are configured to engage with aft radially extending rails (e.g.,aft radially extending rails 418 a, 418 b). The standoff shelves 710,712 extend the full radial length of the leading edge baffle 700 (i.e.,from the outer diameter end 706 to the inner diameter end 708) anddefine channels or slots that are shaped to engage with rails of anairfoil body (e.g., as shown in FIG. 7C). The standoff shelves 710, 712are depressions, grooves, channels or the like that are defined asreduced material thickness of the material of the baffle body 704.

FIG. 7C illustrates an enlarged view of the leading edge baffle 700 asinstalled within an airfoil body 704. In this illustration, the airfoilbody 704 includes a forward radially extending rail 714 and an aftradially extending rail 716. Defined between an interior surface of theairfoil body 702 and an exterior surface of the baffle body 704 andbounded at a forward end by the forward radially extending rail 714 andat an aft end by the aft radially extending rail 716 is a radialextending channel 718. By including such standoff shelves on theexterior surface of the baffle body 704, the height (distance fromexterior surface of baffle body 704 to interior surface of airfoil body702) may be tailored to desired cross-sectional area. Further, suchstandoff shelves 710, 712 can provide for a relatively sealed engagementbetween the baffle body 704 and the airfoil body 702 at the rails 714,716. As such, bleed across the engagement region can be minimized oreliminated by providing a more consistent engagement between the bafflebody 704 and the rails 714, 716.

As shown in FIGS. 7A-7B, the leading edge baffle 700 defines an innerplenum 720 for receiving cooling air, such as from an outer diameterplatform, for example. The inner plenum 720 is defined by an innersurface 722 of the baffle body 704, with an open top end (e.g., at theouter diameter end 706) and a closed or solid bottom end (e.g., at theinner diameter end 708), closed by a cap 724. On the exterior of thebaffle body 704, the standoff shelves 710, 712 define different externalsurfaces of the baffle body 704 therebetween. For example, as shown, ashowerhead channel surface 726 is defined along a forward end of thebaffle body 704 between a pressure side forward standoff shelf 710 a anda suction side forward standoff shelf 710 b. The standoff shelves 710,712 are illustratively shown as reduced material thickness portions ofthe baffle body 704. In other embodiments, such as when the materialthickness of the baffle body 704 does not enable carving out material,the standoff shelves 710, 712 may be formed of a bend or curve in thematerial of the baffle body, such as a bend or curve of sheet metal.

A pressure side channel surface 728 is defined on a pressure side of thebaffle body 704 between the pressure side forward standoff shelf 710 aat a forward end and a pressure side aft standoff shelf 712 a at an aftend of the pressure side channel surface 728. A suction side channelsurface 730 is defined on a suction side of the baffle body 704 betweenthe suction side forward standoff shelf 710 b at a forward end and asuction side aft standoff shelf 712 b at an aft end of the suction sidechannel surface 729. An aft channel surface 732 is defined about the aftexterior surface of the baffle body 704 between the pressure side aftstandoff shelf 712 a and the suction side aft standoff shelf 712 b. Oneor more trailing edge impingement apertures 734 may be formed throughthe aft channel surface 732 of the baffle body 704, as described above.

Turning now to FIG. 8 , a schematic illustration of a portion of anairfoil assembly 800 in accordance with an embodiment of the presentdisclosure is shown. The airfoil assembly 800 includes an airfoil havingan airfoil body 802 and a leading edge baffle having a baffle body 804.The airfoil assembly 800 may be similar to that shown and describedabove. The airfoil body 802 includes a forward radially extending rail806 and an aft radially extending rail 808 that are arranged to defineat least a radially extending channel 810 with a portion of the bafflebody 804. The baffle body 804 includes a forward standoff shelf 812 andan aft standoff shelf 814 that are configured to engage with the forwardradially extending rail 806 and an aft radially extending rail 808,respectively. As described above, the standoff shelves 812, 814 arerecesses or channels formed in the material of the baffle body 804. Inthis embodiment, the size and shape of the standoff shelves 812, 814 areselected to form standoff gaps 816, 818 between the surfaces of thestandoff shelves 812, 814 and the rails 806, 808. The standoff gaps 816,818 may be radial span gaps that extend from an outer diameter end to aninner diameter end of the baffle body 804 and thus providethrough-channels from the outer diameter to the inner diameter. Coolingflow may be passed through the standoff gaps 816, 818, thus providing apressured flow that will prevent bleed from one radial extending channelto an adjacent radially extending channel (e.g., as shown and describedabove) across the rails 806, 808.

Turning now to FIGS. 9A-9B, schematic illustrations of an airfoilassembly 900 in accordance with an embodiment of the present disclosureare shown. The airfoil assembly 900 includes an airfoil body and aleading edge baffle 902 installed within a leading edge cavity of theairfoil body, similar to that shown in FIGS. 4A-4D. However, in thisembodiment, some of the feed apertures are arranged at an inner diameterend of the baffle, thus resulting in some cooling flow that flows fromthe inner diameter end toward the outer diameter end.

The leading edge baffle 902 is arranged within the leading edge cavity.Similar to the above described embodiments, to position the leading edgebaffle 902 within the leading edge cavity, the airfoil body includes anumber of radially extending rails 904, 906 that extend inward from therespective walls of the leading edge cavity. Although FIGS. 9A-9Billustrate a pressure side of the airfoil assembly 900, it will beappreciated that the suction side may include similar features, such asshown and described above. Accordingly, a forward radially extendingrail 904 and an aft radially extending rail 906 are arranged along thepressure side wall, with similar structure present on the suction sidewall.

When the leading edge baffle 902 is arranged within the leading edgecavity, the leading edge cavity is divided into a number of sub-cavitiesand/or channels. For example, a feed cavity is defined within theinterior of the leading edge baffle 902. A showerhead radial channel 908is defined between the interior surface of a leading edge 908 of theairfoil body, an exterior surface of the leading edge baffle 902, andbetween the forward radially extending rails 904. A pressure side radialflow channel 910 is defined between the pressure side wall, an exteriorsurface of the leading edge baffle 902, the forward radially extendingrail 904, and the aft radially extending rail 906. An aft channel 912 isdefined aft of each of the aft radially extending rails 906 along thepressure and suction side walls, an interior rib of the airfoil body,and exterior surfaces of the leading edge baffle 902. The aft channel912 may be a through-flow channel that is open at an inner diameter endto supply cooling air, for example, to an inner diameter platform orother downstream components or cavities of an engine structure.

FIG. 9B illustrates a side elevation view (pressure side) of the leadingedge baffle 902. The leading edge baffle 902 extends radially betweenthe outer diameter end 914 to an inner diameter end 916. In someembodiments, each of the outer diameter end 914 and the inner diameterend 916 may be open or unobstructed to allow airflow therethrough. Inother embodiments, the leading edge baffle 902 may be capped at theinner diameter end 916 to form a plenum to supply cooling flow into thechannels external to the leading edge baffle 902. As shown, the leadingedge baffle 902 includes a number of feed apertures 918, 920, 922. Theleading edge baffle 902 will be fed with cooling air from a platform orother source, as known in the art, and the cooling air will enter thefeed cavity of the baffle and flow into the channels 908, 910, 912defined between the exterior of the leading edge baffle 902 and theinterior surfaces of the airfoil body.

A leading edge feed aperture 918 is arranged on a leading edge end ofthe leading edge baffle 902 and is configured to supply cooling air intothe showerhead radial channel 908. The flow through the leading edgefeed aperture 918 will enter the showerhead radial channel 908, from thefeed cavity, at the inner diameter thereof and then flow radiallyoutward (upward, toward the outer diameter end 914) along the interiorsurface of the leading edge 908 of the airfoil body. The cooling flowwill then exit through one or more showerhead apertures which may expelcooling flow along the exterior of the leading edge 908 of the airfoilbody and provide film cooling thereto.

The pressure side radial flow channel 910 may be fed with cooling flowthrough a pressure side feed aperture arrays 920, with the suction sidehaving a similar configuration. The cooling flow will enter the feedcavity and pass through the side feed aperture arrays 920 to enter therespective channels 908, 910 and flow radially outward (toward the outerdiameter end 914) to provide cooling to the forward portions of each ofthe side walls of the leading edge cavity.

The aft channel 912 may be supplied with cooling from through aft feedaperture arrays 922 (e.g., an array on each of the pressure and suctionsides of the leading edge baffle 902). The cooling flow will enter thefeed cavity and pass through the aft feed aperture arrays 922 to enterthe aft channel 912 and flow radially inward (toward the inner diameterend 916) to provide cooling to the aft portions of each of the pressureside wall and the suction side wall of the leading edge cavity. Feedaperture arrays in accordance with embodiments of the present disclosurecan be adjusted/tailored to optimize fill characteristics andimpingement heat transfer. The feed aperture arrays may serve todistribute flow between channels as desired. For example, the total areaof the feed array for the forward suction side channel may be greaterthan any other channel due to requiring a larger amount of flow to coolthe forward suction side gas path surfaces of the airfoil. Flow splitsbetween channels can allow for further optimization/adjustment if hotspots are noticed and flow can be spared from another channel to addresssuch hot spots.

The aft channel 912 may be substantially fluidly separate from theforward positioned side radial flow channels 910. Such fluid separationmay be provided by the aft radially extending rails 906. Because the aftchannels are fluidly separate from the forward channels, each sectioncan be addressed individually to meet the cooling required for theirrespective heat loads without risk of unexpected cooling imbalance whenone or the other is adjusted. In some embodiments, the aft radiallyextending rails 906 may be solid from a position proximate the outerdiameter end 914 to a position proximate the inner diameter end 916 whenviewed relative to the leading edge baffle 902. In some embodiments,however, one or more cross-over holes may be arranged in the aftradially extending rails 906 to permit some amount of fluidcommunication between the side radial flow channels 910 and the aftchannel 912.

The leading edge baffle 902 is positioned and retained within theleading edge cavity by the radially extending rails 904, 906 and aninner diameter forward collar 924. The inner diameter forward collar 924is a structural feature of the airfoil body, as described above. Theinner diameter forward collar 924 extends from an inner diameter end ofeach of the aft radially extending rails 906 in a forward directiontoward the leading edge 908 of the airfoil body, as shown in FIG. 9B. Asshown, the inner diameter forward collar 924 may provide for an innerdiameter wall or blockage, which prevents throughflow through the sideradial flow channels 910 and/or the showerhead radial channel 908. Thisresults in the air within such channels 908, 910 to be expelled throughthe showerhead apertures and keeps this portion of the airfoil fluidlyseparate from the inner diameter platform and aft leading edge regions.In some embodiments, the leading edge baffle 902 may rest, at leastpartially, upon the inner diameter forward collar 924.

As noted above, the feed apertures 918, 920 are arranged at an innerdiameter end of the leading edge baffle 902. In such a configuration,cooling flow may enter an internal feed cavity of the leading edgebaffle 902 at the outer diameter end 914, then enter the channels 908,910 at the inner diameter end and the flow may then flow radiallyoutward toward the outer diameter end 914 of the leading edge baffle902. The aft channel 912, as in the other embodiments, may remain aradially inward flowing channel. The outward flow in the forwardchannels 910, 908 may be augmented by heat transfer augmentationfeatures and then expelled through one or more showerhead aperturesformed in the leading edge 908 of the airfoil body. In some suchembodiments, the channels 908, 910 may be capped at an outer diameterend thereof or otherwise blocked (e.g., by a portion of a platform) suchthat the flow therein flows out through showerhead apertures or otherapertures formed at the leading edge portions of the airfoil body toexpel cooling flow to an exterior of the airfoil body.

Turning now to FIGS. 10A-10B, schematic illustrations of a leading edgebaffle 1000 in accordance with an embodiment of the present disclosureare shown. FIG. 10A is a cross-sectional view looking radially inward asinstalled in an airfoil 1002, and FIG. 10B is an enlarged detailed viewthereof. The leading edge baffle 1000 may be substantially similar tothat shown and described above, being configured to be installed withina leading edge cavity of an airfoil and define multiple radial flowchannels between the exterior of the leading edge baffle 1000 and theinterior surfaces of the leading edge cavity of the airfoil 1002.

As shown in FIGS. 10A-10B, the leading edge baffle 1000 includes abaffle body 1004 that extends radially between an outer diameter end andan inner diameter end. On the exterior surface of the leading edgebaffle 1000, a number of radially extending rails 1006, 1008 are formedon or with the material of the leading edge baffle 1000. Forwardradially extending rails 1006 are arranged at a forward end of theleading edge baffle 1000 and are configured to engage with the interiorsurface of the airfoil 1002, which may optionally include shelves,grooves, slots, recesses, channels, or the like, such as shown inreverse in FIGS. 7B-7C. Similarly, aft radially extending rails 1008 arearranged aft of the forward radially extending rails 1006 and areconfigured to engage with the interior surface of the airfoil 1002. Ifthe airfoil 1002 includes receiving features, such features may beformed as depressions, grooves, channels or the like that are defined asreduced material thickness of the material of the airfoil 1002 along thehot walls.

As shown in FIGS. 10A-10B, the leading edge baffle 1000 defines an innerplenum 1010 for receiving cooling air, such as from an outer diameterplatform, for example. The inner plenum 1010 is defined by an innersurface 1012 with an open end (e.g., at the outer diameter end) and aclosed or solid opposite end (e.g., at the inner diameter end), whichmay be closed by a cap or the like. On the exterior of the leading edgebaffle 1000, the radially extending rails 1006, 1008 extend outwardtherefrom to engage with the inner surface of the airfoil 1002. Theleading edge baffle 1000 may include a showerhead channel surfacedefined along a forward end of the leading edge baffle 1000, similar tothat described above. Similarly, pressure and suction side channelsurface may be defined on respective pressure and suction sides of theleading edge baffle 1000, as described above. An aft channel surface maybe defined about the aft exterior surface of the leading edge baffle1000. The leading edge baffle 1000 may include shower head apertures,impingement apertures, or the like, distributed or arranged about theleading edge baffle 1000 to provide cooling flow and other functions, asdescribed above.

Although illustrated herein with substantially linear standoff rails andassociated features (whether on the airfoil body or the baffle body),such geometry is not intended to be limiting. For example, the rails,recesses, shelves and other radially extending features described hereinand provided a standoff functionality may have curved, curvilinear,and/or discontinuous geometries. Furthermore, the standoff rails andassociated optional receiving structures, and the gaps defined thereby,may each be tailored in geometry, shape, orientation, and the like, inthe radial, axial, and/or circumferential direction(s) to optimize localpressure loss and internal convective heat transfer characteristics. Thestandoff rail height and baffle gap height may be tailored both radiallyand axially to optimize local pressure loss and internal convective heattransfer characteristics.

It will be appreciated that the shape, size, and aspect ratio of thestandoff rails (whether on the airfoil body or the baffle body) may havedifferent shapes, sizes, and aspect ratios than that illustrated anddescribed above. That is, the disclosed, described, and illustratedembodiments are intended to be informative and not limiting to thefeatures of the disclosed embodiments and implementations thereof. Forexample, the standoff rail geometry, height, width, and shape may bedictated by local fin efficiency requirements. In other words, it may bepreferable to ensure that the standoff rails do not result in a localhot spot. The standoff rail geometry limitations may be driven by localexternal local heat flux, backside convection, and external airfoil wallthickness requirements. In accordance with some embodiments, and withoutlimitation, the height and width of the standoff rails can range between0.2 times to 3 times the local wall thickness of the respectivecomponent (e.g., airfoil or baffle). That is, in a direction extendingbetween the baffle surface and the airfoil surface, the standoff railsmay have a thickness greater than the local thickness of the respectivecomponent that does not include such standoff rail. For example, andwithout limitation, the thickness of the standoff rails in an extensiondirection may be a distance of between 20% and 300% of the localcomponent wall thickness.

Advantageously, embodiments described herein provide for improvedcooling schemes for airfoils used in gas turbine engines. The coolingschemes include a relatively large leading edge cavity defined within anairfoil body and a space-eater baffle installed therein. The baffle canbe fed with cooling air that is directed into radial extending channelsthat are defined between the exterior surface of the baffle and theinterior surfaces of the airfoil. Forward radially extending rails canbe segmented such that flow from pressure side and suction side radialflow channels into a showerhead radial channel that is defined radiallyalong the leading edge of the airfoil. The air within the showerheadradial channel may be expelled to the exterior of the airfoil throughshowerhead apertures. This provides a pressure differential to pullcooling flow from the pressure side and suction side radial flowchannels into the showerhead radial channel. Aft of the pressure sideand suction side radial flow channels may be an aft radial flow channelthat is a pass-through channel that directs cooling flow along thepressure and suction side walls and then into an inner diameter platformof the airfoil. Further, in some embodiments, flow can be expelled intothe gaspath at various locations along the pressure side and/or suctionside, if necessary, to address additional areas with film withoutcompromising the overall effectiveness of the configuration orshowerhead region cooling.

In some embodiments, trailing edge impingement apertures may be formedon or in an aft wall of the leading edge baffle. As such, cooling flowfrom within the leading edge baffle may be impinged upon an interior ribof the airfoil, thus preventing migration between radial cooling flowsalong the hot walls of the airfoil. Further, in some embodiments, aninner diameter forward collar may be formed as part of the airfoil bodyand provide support for the leading edge baffle and/or blockage ofradial flow, such that through-flow is prevented at the inner diameterof radial flow channels that terminate at the inner diameter forwardcollar.

As used herein, the terms “about” and “substantially” are intended toinclude the degree of error associated with measurement of theparticular quantity based upon the equipment available at the time offiling the application. For example, “about” or “substantially” mayinclude a range of ±8%, or 5%, or 2% of a given value or otherpercentage change as will be appreciated by those of skill in the artfor the particular measurement and/or dimensions referred to herein.Further, when used with respect to a non-numerical feature, such termsencompass the variability within the bounds of manufacturing,measurement, or understanding within the knowledge and experience ofthose of skill in the art. The terminology used herein is for thepurpose of describing particular embodiments only and is not intended tobe limiting of the present disclosure. As used herein, the singularforms “a,” “an,” and “the” are intended to include the plural forms aswell, unless the context clearly indicates otherwise. It will be furtherunderstood that the terms “comprises” and/or “comprising,” when used inthis specification, specify the presence of stated features, integers,steps, operations, elements, and/or components, but do not preclude thepresence or addition of one or more other features, integers, steps,operations, element components, and/or groups thereof. It should beappreciated that relative positional terms such as “forward,” “aft,”“upper,” “lower,” “above,” “below,” “radial,” “axial,”“circumferential,” and the like are with reference to normal operationalattitude and should not be considered otherwise limiting.

While the present disclosure has been described with reference to anillustrative embodiment or embodiments, it will be understood by thoseskilled in the art that various changes may be made and equivalents maybe substituted for elements thereof without departing from the scope ofthe present disclosure. In addition, many modifications may be made toadapt a particular situation or material to the teachings of the presentdisclosure without departing from the essential scope thereof.Therefore, it is intended that the present disclosure not be limited tothe particular embodiment disclosed as the best mode contemplated forcarrying out this present disclosure, but that the present disclosurewill include all embodiments falling within the scope of the claims.

What is claimed is:
 1. An airfoil assembly for a gas turbine engine, theairfoil assembly comprising: an airfoil body having a leading edge, atrailing edge, a pressure side wall, and a suction side wall, theairfoil body extending in a radial direction between an outer diameterend and an inner diameter end, wherein the airfoil defines a leadingedge cavity bounded by interior surfaces of the airfoil body along theleading edge, the pressure side wall, the suction side wall, and aninterior rib extending between the pressure side wall and the suctionside wall; a leading edge baffle installed within the leading edgecavity; a first forward radially extending rail extending into theleading edge cavity and extending between the inner diameter end and theouter diameter end in a radial direction, the first forward radiallyextending rail positioned on the pressure side wall of the airfoil body;a second forward radially extending rail extending into the leading edgecavity and extending between the inner diameter end and the outerdiameter end in the radial direction, the second forward radiallyextending rail positioned on the suction side wall of the airfoil body;a first aft radially extending rail extending into the leading edgecavity and extending between the inner diameter end and the outerdiameter end in the radial direction, the first aft radially extendingrail positioned on the pressure side wall of the airfoil body; and asecond aft radially extending rail extending into the leading edgecavity and extending between the inner diameter end and the outerdiameter end in the radial direction, the second aft radially extendingrail positioned on the suction side wall of the airfoil body, wherein:each of the first and second forward radially extending rails aresegmented in the radial direction, a showerhead radial channel isdefined between an interior surface of the airfoil body along theleading edge, an exterior surface of the leading edge baffle, and eachof the first and second forward radially extending rails, a pressureside radial flow channel is defined between an interior surface of theairfoil body along the pressure side wall, an exterior surface of theleading edge baffle, the first forward radially extending rail, and thefirst aft radially extending rail, a suction side radial flow channel isdefined between an interior surface of the airfoil body along thesuction side wall, an exterior surface of the leading edge baffle, thesecond forward radially extending rail, and the second aft radiallyextending rail, and an aft channel is defined between an interiorsurface of the airfoil body along the suction side wall, the pressureside wall, and the interior rib, an exterior surface of the leading edgebaffle, and the first and second aft radially extending rails.
 2. Theairfoil assembly of claim 1, further comprising a plurality ofshowerhead apertures formed on the leading edge, pressure side, orsuction side of the airfoil body and fluidly connected to theshowerhead, pressure side, or suction side radial flow channels.
 3. Theairfoil assembly of claim 1, further comprising one or more heattransfer augmentations features arranged on an interior surface of theairfoil body along at least one of the showerhead radial channel, thepressure side radial flow channel, the suction side radial flow channel,or the aft channel.
 4. The airfoil assembly of claim 1, wherein theleading edge baffle comprises an aft wall having at least one trailingedge impingement aperture arranged to direct an impingement flow againstthe interior rib of the airfoil body.
 5. The airfoil assembly of claim1, further comprising an inner diameter forward collar formed about aportion of the inner diameter end of the leading edge cavity.
 6. Theairfoil assembly of claim 5, wherein the inner diameter forward collardefines a blockage of at least one of the showerhead radial channel, thepressure side radial flow channel, and the suction side radial flowchannel to prevent radial through-flow at the inner diameter endthereof.
 7. The airfoil assembly of claim 5, wherein the inner diameterforward collar is configured to direct air flow at the inner diameterend of the airfoil body from at least one of the pressure side radialflow channel or the suction side radial flow channel into the showerheadradial channel.
 8. The airfoil assembly of claim 1, wherein the leadingedge baffle is capped at an inner diameter end thereof.
 9. The airfoilassembly of claim 1, wherein the aft channel is a throughflow channelconfigured to supply cooling flow into at least an inner diameterplatform.
 10. The airfoil assembly of claim 1, wherein the leading edgebaffle comprises a leading edge feed aperture at an outer diameter endthereof, the leading edge feed aperture configured to direct a coolingflow into the showerhead radial channel at an outer diameter endthereof.
 11. The airfoil assembly of claim 1, wherein the leading edgebaffle comprises at least one side feed aperture array at an outerdiameter end thereof, the at least one side feed aperture arrayconfigured to direct a cooling flow into at least one of the pressureside radial flow channel or the suction side radial flow channel at anouter diameter end thereof.
 12. The airfoil assembly of claim 11,further comprising at least one resupply aperture on the leading edgebaffle arranged at a position between the at least one side feedaperture array and the inner diameter end of the leading edge baffle.13. The airfoil assembly of claim 1, wherein the leading edge bafflecomprises at least one aft feed aperture array at an outer diameter endthereof, the at least one aft feed aperture array configured to direct acooling flow into the aft channel at an outer diameter end thereof. 14.The airfoil assembly of claim 1, wherein the leading edge bafflecomprises a solid portion between at least one feed aperture proximatean outer diameter end of the leading edge baffle and an inner diameterend of the leading edge baffle.
 15. The airfoil assembly of claim 1,wherein the leading edge baffle comprises at least one standoff shelfconfigured to engage with at least one of the first forward radiallyextending rail, the second forward radially extending rail, the firstaft radially extending rail, or the second aft radially extending rail.16. The airfoil assembly of claim 15, wherein a standoff gap is formedbetween the at least one standoff shelf and the respective rail to whichthe at least one standoff shelf engages.
 17. The airfoil assembly ofclaim 16, wherein the standoff gap defines a throughflow channel forcooling air.
 18. The airfoil assembly of claim 1, wherein each of thefirst and second aft radially extending rails are substantiallycontinuous in the radial direction and provide fluid separation betweenthe aft channel and the other channels of the leading edge cavity. 19.The airfoil assembly of claim 1, wherein the leading edge bafflecomprises a leading edge feed aperture at an inner diameter end thereof,the leading edge feed aperture configured to direct a cooling flow intothe showerhead radial channel at an inner diameter end thereof.
 20. Theairfoil assembly of claim 1, wherein the leading edge baffle comprisesat least one side feed aperture array at an inner diameter end thereof,the at least one side feed aperture array configured to direct a coolingflow into at least one of the pressure side radial flow channel or thesuction side radial flow channel at an inner diameter end thereof.